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21. 发明授权

US11926416B1 Flight control systems and related methods of magnetically counteracting aerodynamic lift forces on flight control surfaces 有权
公开(公告)号：US11926416B1
公开(公告)日：2024-03-12
申请号：US17891013
申请日：2022-08-18
申请人： The Boeing Company
发明人： Kevin Raylin Tsai
IPC分类号： B64C9/20 , B64C13/24 , B64C9/14
CPC分类号： B64C9/20 , B64C13/24 , B64C2009/143
摘要： Methods comprise flying an aircraft at cruise which results in an aerodynamic lift force on a flight control surface of the aircraft that urges the flight control surface away from a stowed position. Concurrently with the flying, the methods include counteracting the aerodynamic lift force with a magnetic force that urges the flight control surface towards the stowed position and that results in the flight control surface being maintained in the stowed position during the flying. Flight control systems comprise a flight control surface and an adjacent structure. The flight control surface or the adjacent structure comprises a magnet and the other of the flight control surface or the adjacent structure comprises a ferromagnetic structure. A magnetic force urges the flight control surface toward a stowed position.

22. 发明授权

US10000276B2 Pushing device, moving mechanism and aircraft 有权
公开(公告)号：US10000276B2
公开(公告)日：2018-06-19
申请号：US15134711
申请日：2016-04-21
申请人： AIRBUS (BEIJING) ENGINEERING CENTRE COMPANY LIMITED
发明人： Ming Li , Yumin Sun
IPC分类号： B64C13/28 , B64C9/16 , B64C13/00 , B64C13/42 , B64C9/14 , F03G1/10
CPC分类号： B64C13/341 , B64C9/14 , B64C9/16 , B64C13/00 , B64C2009/143 , F03G1/10
摘要： The present application relates to a pushing device, a moving mechanism and an aircraft. According to an aspect of the present application, a pushing device for a moving mechanism of an aircraft is provided, the moving mechanism including a primary moving device and an auxiliary moving device assisting the primary moving device, the pushing device including a support member and a pushing assembly supported by the support member, and the pushing assembly including a pushing element and an energy storage element. The pushing element is adapted to push a broken part of the auxiliary moving device to an offset position from a normal working position by means of energy from the energy storage element when the auxiliary moving device breaks. According to the present application, it is possible to provide an effective fault protection to the moving mechanism of the aircraft.

23. 发明申请

US20180118329A1 WING FOR AN AIRCRAFT HAVING A SIMPLIFIED MOVABLE AERODYNAMIC SURFACE AND A FLEXIBLE SEALING 审中-公开
公开(公告)号：US20180118329A1
公开(公告)日：2018-05-03
申请号：US15718974
申请日：2017-09-28
申请人： Airbus Operations GmbH
发明人： Bernhard SCHLIPF , Dort DAANDELS
IPC分类号： B64C9/02
CPC分类号： B64C9/02 , B64C9/14 , B64C2009/143
摘要： A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. The sealing device includes a flexible sealing body, which seals the intermediate space between the high lift body and the wing structure in extended positions of the high lift body.

24. 发明授权

US09789955B1 High-lift device of air vehicle 有权
公开(公告)号：US09789955B1
公开(公告)日：2017-10-17
申请号：US15629407
申请日：2017-06-21
申请人： THE SOCIETY OF JAPANESE AEROSPACE COMPANIES , KAWASAKI JUKOGYO KABUSHIKI KAISHA
发明人： Kazuhide Isotani , Kenji Hayama
IPC分类号： B64C3/58 , B64C21/08
CPC分类号： B64C21/08 , B64C3/50 , B64C9/02 , B64C9/18 , B64C2009/143 , B64C2230/14 , Y02T50/166
摘要： A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.

25. 发明申请

US20170001712A1 FORE FLAP DISPOSED ON THE WING OF AN AIRCRAFT 审中-公开
标题翻译：在飞机的翅膀上出现的飞轮
公开(公告)号：US20170001712A1
公开(公告)日：2017-01-05
申请号：US15202362
申请日：2016-07-05
申请人： Airbus Operations GmbH
发明人： Bernhard SCHLIPF , Xavier HUE
IPC分类号： B64C9/24 , B64C3/50
CPC分类号： B64C9/24 , B64C3/50 , B64C2009/143
摘要： A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high- energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.
摘要翻译：一架安排在飞机机翼上的前沿板条。前缘板条设置在主翼的前部。前缘板条具有部分延伸的设置，其后缘平坦于机翼，并且进一步延伸设置，其后缘与机翼的鼻部间隔开，以打开从下表面供给高能空气的间隙的板条到机翼的上表面。前缘板条包括一个主体和一个面向主翼的后缘，它可相对于主体围绕板条的翼展方向弯曲，并且在其上设置板条的后缘，并且通过加载产生接触力的装置用于使板条的后缘与机翼的轮廓鼻之间接触。

26. 发明申请

US20150353187A1 LEADING EDGE ASSEMBLY FOR AN AIRCRAFT 审中-公开
标题翻译：飞机前沿组装
公开(公告)号：US20150353187A1
公开(公告)日：2015-12-10
申请号：US14266063
申请日：2014-04-30
申请人： The Boeing Company
发明人： Clayton A. Smith
IPC分类号： B64C9/34 , B64C13/36
CPC分类号： B64C9/34 , B64C9/22 , B64C13/36 , B64C2009/143 , Y02T50/32
摘要： A wing assembly includes a main wing and a slat movable between stowed and deployed positions. The main wing includes a panel movable to a retracted position when the slat is in the stowed position, such that the slat outer surface and a wing upper surface define a first continuous outer mold line shape. The panel may further be movable to an extended position when the slat is in the deployed position, such that an outer surface of the panel and the wing upper surface define a second continuous outer mold line shape.
摘要翻译：翼组件包括主翼和可在收起位置和展开位置之间移动的板条。主翼包括当板条处于收起位置时可移动到缩回位置的板，使得板条外表面和机翼上表面限定第一连续的外模线形状。当板条处于展开位置时，面板还可以移动到延伸位置，使得面板的外表面和机翼上表面限定第二连续的外模线形状。

27. 发明授权

US09016638B2 Aircraft flap system and associated method 有权
标题翻译：飞机襟翼系统及相关方法
公开(公告)号：US09016638B2
公开(公告)日：2015-04-28
申请号：US13623533
申请日：2012-09-20
申请人： The Boeing Company
发明人： Bruce A. Dahl , Gene A. Quandt
IPC分类号： B64C9/00 , B64C9/20 , B64C9/32 , B64C9/14
CPC分类号： B64C9/20 , B64C9/323 , B64C2009/143 , Y02T50/32
摘要： An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap and a panel pivotally attached to the first flap, such as to a rearward portion of the first flap. The aircraft flap system also includes an actuator configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap, thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap, thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.
摘要翻译：提供飞行器翼片系统和相关联的方法以便于地面滚动破碎而不损害飞行性能。飞行器翼片系统包括第一翼片和枢转地附接到第一翼片的面板，例如到第一翼片的后部。飞行器翼片系统还包括致动器，该致动器被配置为将面板可控地定位在收起位置和展开位置。在收起位置，面板作为第一挡板的延续部，从而有助于在飞行期间由第一挡板提供的升力。相反，在展开位置，面板相对于第一挡板铰接，从而减少或消除由飞行器着陆后由挡板提供的电梯。

28. 发明授权

US08864083B1 Low noise wing slat system with a fixed wing leading edge and deployable bridging panels 有权
标题翻译：具有固定翼前缘和可部署桥接板的低噪声翼板系统
公开(公告)号：US08864083B1
公开(公告)日：2014-10-21
申请号：US12751514
申请日：2010-03-31
申请人： Arvin Shmilovich , Yoram Yadlin
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： B64C3/50
CPC分类号： B64C9/24 , B64C2009/143 , Y02T50/32
摘要： Concepts and technologies described herein provide for a low noise aircraft wing slat system. According to one aspect of the disclosure, a wing slat is used in conjunction with upper and lower bridging elements to minimize airframe noise associated with a high lift system during takeoff and landing flight operations. An upper bridging element deploys from a slat or an aircraft wing during deployment of the slat for takeoff operations and creates a continuous aerodynamic surface between the slat and an upper surface of the wing leading edge to improve the airflow and reduce drag. A lower bridging element deploys from the wing during cruise flight to bridge a gap between a lower surface of a stowed leading edge slat and a lower surface of the wing. During landing operations, both upper and lower bridging elements remain stowed to optimize ambient airflow for noise abatement and lift creation.
摘要翻译：本文所述的概念和技术提供了一种低噪声飞机翼板系统。根据本公开的一个方面，机翼板条与上部和下部桥接元件结合使用，以使起飞和着陆飞行操作期间与高升力系统相关联的机身噪音最小化。上部桥接元件在用于起飞操作的板条部署期间从板条或飞机机翼部署，并且在板条和机翼前缘的上表面之间产生连续的空气动力学表面，以改善气流并减少阻力。在巡航飞行期间，下桥接元件从机翼部署，以桥接收起的前缘板条的下表面和机翼的下表面之间的间隙。在着陆操作期间，上部和下部桥接元件保持收起，以优化环境气流，以减少噪音和提升产生。

29. 发明申请

US20140077038A1 AIRCRAFT FLAP SYSTEM AND ASSOCIATED METHOD 有权
标题翻译：飞机襟翼系统及相关方法
公开(公告)号：US20140077038A1
公开(公告)日：2014-03-20
申请号：US13623533
申请日：2012-09-20
申请人： Bruce A. Dahl , Gene A. Quandt
发明人： Bruce A. Dahl , Gene A. Quandt
IPC分类号： B64C9/20
CPC分类号： B64C9/20 , B64C9/323 , B64C2009/143 , Y02T50/32
摘要： An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap and a panel pivotally attached to the first flap, such as to a rearward portion of the first flap. The aircraft flap system also includes an actuator configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap, thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap, thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.
摘要翻译：提供飞行器翼片系统和相关联的方法以便于地面滚动破碎而不损害飞行性能。飞行器翼片系统包括第一翼片和枢转地附接到第一翼片的面板，例如到第一翼片的后部。飞行器翼片系统还包括致动器，该致动器被配置为将面板可控地定位在收起位置和展开位置。在收起位置，面板作为第一挡板的延续部，从而有助于在飞行期间由第一挡板提供的升力。相反，在展开位置，面板相对于第一挡板铰接，从而减少或消除由飞行器着陆后由挡板提供的电梯。

30. 发明授权

US08596586B2 High-lift system for an aircraft, method for displacing a lift flap, and aircraft having a high-lift system 有权
标题翻译：用于飞行器的高升力系统，用于移动升降机挡板的方法以及具有高升程系统的飞机
公开(公告)号：US08596586B2
公开(公告)日：2013-12-03
申请号：US13490009
申请日：2012-06-06
申请人： Karsten Schroeder
发明人： Karsten Schroeder
IPC分类号： B64C3/50
CPC分类号： B64C9/24 , B64C2009/143 , Y02T50/32
摘要： A high lift system is provided for an aircraft. The high lift system includes, but is not limited to a lift flap arranged on a wing and coupled to the wing so as to be movable relative to the wing, between a retracted position and at least one extended position. In the retracted position the lift flap rests against the wing, and in an extended position forms an air gap to the wing. The lift flap directed towards its trailing edge comprises at least one region of variable curvature, which region in an extended position of the lift flap extends towards the wing.
摘要翻译：飞机提供了高升程系统。高升降系统包括但不限于设置在机翼上并联接到机翼上以便在缩回位置和至少一个延伸位置之间相对于机翼移动的升降挡板。在缩回位置，提升翼片靠在机翼上，并且在延伸位置形成与机翼的气隙。指向其后缘的升降翼包括至少一个可变曲率的区域，该提升翼的延伸位置中的该区域向翼延伸。

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